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특허 상세정보

Gas turbine engine exhaust nozzle having a noise attenuation device driven by shape memory material actuators

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02F-003/02   
미국특허분류(USC) 060/226.1; 060/262
출원번호 US-0950551 (2004-09-28)
우선권정보 GB-0105349(2001-03-03)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Manelli Denison &
인용정보 피인용 횟수 : 18  인용 특허 : 8
초록

A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises an actuation mechanism capable of moving the tabs between a first deployed position, where the tabs interact with a gas stream to reduce exhaust noise thereof, and a second non-deployed position, where the tabs are substantially aerodynamically unobtr...

대표
청구항

We claim: 1. A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle, a downstream portion and a plurality of tabs, each tab extending in a generally axial direction from the downstream portion of the nozzle wherein the nozzle further comprises an actuation mechanism capable of moving the tabs between a first deployed position, with in the first position the tabs interacting with a gas stream to reduce exhaust noise thereof, and a second non-deplo...

이 특허를 인용한 특허 피인용횟수: 18

  1. Viswanathan,Krishnamurthy. Apparatus and method for reduction jet noise from single jets. USP2008057377108.
  2. Viswanathan, Krishnamurthy. Apparatus and method for reduction of jet noise from single jets. USP2010087784285.
  3. Viswanathan, Krishnamurthy. Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flaws. USP2010117836700.
  4. Viswanathan,Krishnamurthy. Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flows. USP2008057377109.
  5. Narayanan, Satish; Simonich, John; Schlinker, Robert Hans. Asymmetric serrated nozzle for exhaust noise reduction. USP2009047520124.
  6. Core, Robert A.. Dilating fan duct nozzle. USP2010057716932.
  7. Baran, Kenneth C.. Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system. USP2010057721549.
  8. Sellers, Benjamin J.; Tulip, Paul R.; Roberts, Alastair P.; Bacon, Richard P.. Flow modulating device. USP2014028651142.
  9. Chanez, Philippe Gerard; Zeggai, Kamel. Gas exhaust nozzle for a bypass turbomachine having an exhaust or throat section that can be varied by moving the secondary cowl. USP2009107600384.
  10. Webster, John R. Gas turbine engine exhaust nozzle. USP2009087578132.
  11. Baltas, Constantine; Hauser, Joseph R.. Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method. USP2012098256225.
  12. Alletzhauser, Eric W.. Gas turbine engine with fan variable area nozzle having a rotational valve system. USP2011067966827.
  13. Do, Logan H.; Krystowski, Edward A.. Gas turbine engine with variable area fan nozzle. USP2013108549834.
  14. Bakken, David Alan. Methods and apparatus for sealing variable area fan nozzles of jet engines. USP2018069989009.
  15. Lynch, Michael D.; Barr, Dustin C.. Nozzle with temperature-responsive throat diameter. USP2010077762078.
  16. Wood,Jeffrey H. Shape changing structure. USP2007057216831.
  17. Blodgett,Keith Edward James; Early,Kevin Sean; Martens,Steven; Bailey,William Andrew; Price,Kenneth Daniel. Sinuous chevron exhaust nozzle. USP2007127305817.
  18. Baltas, Constantine; Ali, Amr. Variable fan nozzle using shape memory material. USP2016059328695.